Thermal insulation compartment device and temperature adjustment method thereof

Abstract

The application relates to the technical field of aero-engine testing, and discloses a heat insulation cabin device and a temperature adjusting method thereof. The heat insulation cabin device comprises a heat insulation cabin body, an upper cabin cover and a lower cabin body, the upper cabin cover and the lower cabin body jointly enclose a heat insulation cabin room, the lower cabin body is provided with a first wall body and a second wall body, the first wall body and the second wall body are spaced apart to form an air flow channel, the lower cabin body is provided with a flow channel inlet and a flow channel outlet, one end of the flow channel inlet is connected with the air flow channel, and the other end is connected with the heat insulation cabin room; one end of the flow channel outlet is connected with the air flow channel, and the other end is connected with a blower; and the lower cabin body is further provided with a cold air compensation interface, one end of the cold air compensation interface is connected with the heat insulation cabin room, and the other end is connected with a cold air source. The heat insulation cabin device can ensure that a power measurement system normally works in high-temperature and low-temperature environment testing of a turboshaft engine.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine test, in particular to a heat insulation cabin device and a temperature adjusting method thereof. BACKGROUND

[0002] Before the type approval of a turboshaft engine, high and low temperature environment tests need to be completed, among which, in the technical identification test, an engine vibration measurement test needs to be completed, in which the engine is operated at the maximum inlet temperature; in the type approval test, high and low temperature starting and acceleration tests need to be completed, in the low temperature test, the engine needs to be started after being immersed in an environment temperature of-54℃ for 10 hours, and in the high temperature test, the engine needs to be started after being immersed in an environment temperature of 71℃ for 10 hours. At present, the high and low temperature environment tests are usually completed on an altitude simulation test bench or a starting rule test vehicle bench, in which a water power absorber is used to absorb and measure the output shaft power of the engine, and a flywheel is used to simulate the output shaft speed inertia moment of the engine, and the water power absorber and the flywheel are collectively referred to as a power measurement system. However, in the prior art, the power measurement system cannot work normally in the high and low temperature environment tests of the turboshaft engine. SUMMARY

[0003] Therefore, the present application provides a heat insulation cabin device and a temperature adjusting method thereof to solve the problem that the power measurement system cannot work normally in the high and low temperature environment tests of the turboshaft engine in the prior art.

[0004] In a first aspect, the present application provides a heat insulation cabin device, comprising:

[0005] A heat insulation cabin body, comprising an upper cabin cover and a lower cabin body, the upper cabin cover and the lower cabin body jointly enclose a heat insulation cabin room, and the heat insulation cabin room is used for accommodating a power measurement system;

[0006] The lower cabin body has a first wall body and a second wall body arranged at intervals, the first wall body is arranged on the side of the second wall body facing the heat insulation cabin room, and the side of the first wall body away from the heat insulation cabin room is spaced apart from the second wall body to form an air flow channel;

[0007] The lower cabin body is provided with a flow channel inlet, which is a flywheel cooling port, one end of the flow channel inlet is in communication with the air flow channel, and the other end is in communication with the heat insulation cabin room; the lower cabin body is also provided with a flow channel outlet, one end of the flow channel outlet is in communication with the air flow channel, and the other end is in communication with a blower;

[0008] The lower cabin body is also provided with a cold air compensation interface, one end of the cold air compensation interface is in communication with the heat insulation cabin room, and the other end is in communication with a cold air source.

[0009] Beneficial Effects: The heat insulation chamber device provided by this invention, during low-temperature environment testing, uses a low-temperature environment simulated by a starting test bench, typically -60℃ to -10℃, outside the heat insulation chamber. The heat insulation chamber is connected to the atmosphere of the test chamber. The lower chamber is equipped with an air flow channel, a flow channel inlet, and a flow channel outlet. The flow channel inlet is a flywheel heat dissipation vent, and the flow channel outlet is connected to a blower. When the blower operates, the atmosphere from the test chamber enters the heat insulation chamber, then enters the flywheel, and then enters the air flow channel through the flow channel inlet, transferring heat to the lower chamber. The heat is then drawn away by the blower through the flow channel outlet. During this process, the equipment heat dissipates through the flow channel inlet, passes through the air flow channel, and is drawn away by the blower. The air dissipates heat as it passes through the air flow channel, providing a certain degree of insulation for the insulation layer, thereby ensuring that the temperature inside the heat insulation chamber remains at room temperature. The ambient temperature is typically 23℃±5℃, thus solving the problem of the dynamometer not working properly in low-temperature environments. During high-temperature environmental testing, due to the high-temperature environment simulated by the starting test bench and the heat dissipation from friction between the dynamometer and the flywheel, the temperature inside the heat-insulated compartment usually reaches 60℃. By setting a cold air compensation interface in the lower compartment, the cold air source is connected to the heat-insulated compartment through the cold air compensation interface, so that the cold air mixes with the hot air inside the heat-insulated compartment to a normal temperature (typically 23℃±5℃), and then passes through the flow channel inlet, air flow channel and flow channel outlet in sequence, and is finally drawn away by the blower. This solves the problem of the flywheel bearing temperature being too high to conduct the test during high-temperature environmental testing, and ensures the normal operation of the power measurement system in high and low temperature environmental tests of turboshaft engines.

[0010] In one alternative embodiment, the upper hatch and the lower hull are disposed opposite each other along a third direction; the upper hatch and the lower hull are connected by bolts and / or screws;

[0011] The lower compartment includes a first sub-compartment and a second sub-compartment, which are symmetrically arranged along a first direction; the first sub-compartment and the second sub-compartment are connected by bolts and / or screws.

[0012] Beneficial effects: By designing the heat insulation chamber body as a structure in which the upper cover and the lower chamber are detachably connected, and the lower chamber is designed as a structure in which the first sub-chamber and the second sub-chamber are detachably connected, the difficulties in disassembly and assembly caused by the overall processing of the chamber are avoided, which greatly saves the time for equipment disassembly, assembly and maintenance, and improves the efficiency of equipment disassembly and assembly.

[0013] In one alternative implementation, the upper hatch and the lower hull are connected by a handle bolt.

[0014] Beneficial effects: The disassembly and assembly operations are convenient, which facilitates the rapid installation and disassembly of the upper hatch and the lower hull, and shortens the disassembly and assembly time.

[0015] In one optional embodiment, a first sealing element is provided between the first sub-cabinet and the second sub-cabinet, the first sealing element being used to seal the first sub-cabinet and the second sub-cabinet.

[0016] The second sealing member is arranged between the upper hatch cover and the lower cabin body and is used to seal the upper hatch cover and the lower cabin body.

[0017] Beneficial effect: Avoids leakage between the first sub-cabin body and the second sub-cabin body and between the upper hatch cover and the lower cabin body when connected, thereby ensuring the sealing of the thermal insulation cabin.

[0018] In an optional embodiment, the second sealing member includes a first layer of sealing and a second layer of sealing, which form a double-layer sealing between the upper hatch cover and the lower cabin body.

[0019] Beneficial effect: Thus effectively avoiding leakage between the upper hatch cover and the lower cabin body when connected, thereby ensuring the sealing of the thermal insulation cabin.

[0020] In an optional embodiment, the first sub-cabin body and the second sub-cabin body each include a first wall body and a second wall body arranged at intervals, and an air flow channel is formed at intervals between the first wall body and the second wall body.

[0021] The first sub-cabin body and the second sub-cabin body each are provided with a flow channel inlet and a flow channel outlet.

[0022] The thermal insulation cabin device further includes a tee joint for connecting the flow channel outlet and the air blower.

[0023] Beneficial effect: By arranging the tee joint to connect the flow channel outlets of the first sub-cabin body and the second sub-cabin body and the air blower, the air blower can act on the air flow channels of the first sub-cabin body and the second sub-cabin body at the same time, which is conducive to enhancing the air flow effect in the first sub-cabin body and the second sub-cabin body.

[0024] In an optional embodiment, the power measurement system includes a flywheel connected to the output shaft of the turboshaft engine.

[0025] The thermal insulation cabin body is provided with a port; the thermal insulation cabin device further includes a sealing assembly arranged at the port.

[0026] The sealing assembly includes a sealing pressing plate and a sealing ring, the sealing pressing plate is connected to the thermal insulation cabin body by bolts and / or screws, and the sealing ring is connected to the sealing pressing plate by bolts and / or screws; the sealing ring is provided with a grid structure.

[0027] The output shaft of the turboshaft engine passes through the sealing ring and is connected to the flywheel.

[0028] Beneficial effects: Because the internal pressure of the heat insulation cabin is higher than the external environment pressure, in order to prevent the normal temperature air in the heat insulation cabin from leaking into the test room, the sealing plate and the sealing ring are arranged at the port of the heat insulation cabin body, so that the output shaft of the turboshaft engine passes through the sealing ring to be connected with the flywheel, wherein the sealing ring is provided with a labyrinth structure, so as to realize the labyrinth sealing, and thus the sealing performance of the heat insulation cabin is ensured, and the normal temperature air in the heat insulation cabin is prevented from leaking into the test room.

[0029] In an optional embodiment, the heat insulation cabin body is further provided with a calibration interface;

[0030] The heat insulation cabin device further comprises a sight glass arranged at the calibration interface.

[0031] Beneficial effects: By arranging the sight glass at the calibration interface of the heat insulation cabin body, the running state of the power measurement system in the heat insulation cabin can be observed through the sight glass.

[0032] In an optional embodiment, the side of the heat insulation cabin body away from the heat insulation cabin is provided with a plurality of reinforcing ribs;

[0033] A thermal insulation layer is filled between the adjacent two reinforcing ribs;

[0034] A plastic spraying layer is arranged on the side of the thermal insulation layer away from the heat insulation cabin body.

[0035] Beneficial effects: By filling the thermal insulation layer between the adjacent two reinforcing ribs, the heat preservation effect of the heat insulation cabin body is ensured; by performing the plastic spraying treatment on the side of the thermal insulation layer away from the heat insulation cabin body to form the plastic spraying layer, the thermal insulation layer is prevented from being sucked into the engine air inlet due to falling off.

[0036] In a second aspect, the application further provides a temperature adjusting method of the heat insulation cabin device, comprising:

[0037] When tested under the first temperature T1 condition, the heat insulation cabin is in communication with the atmosphere of the test room, the flow channel inlet is the flywheel heat dissipation port, the flow channel outlet is connected with the air blower through the three-way piece, the air blower works, the atmosphere of the test room enters the heat insulation cabin, then enters the flywheel, and then enters the air flow channel through the flow channel inlet, so as to transmit heat to the lower cabin body, and then the heat is collected by the three-way piece and is drawn away by the air blower, so as to ensure that the atmosphere in the heat insulation cabin is normal temperature; wherein the value range of T1 is -60℃≤T1≤-10℃.

[0038] When tested under the second temperature T2 condition, the cold air source is connected into the heat insulation cabin through the cold air compensation interface, and is mixed with the hot air in the heat insulation cabin to be normal temperature, and then enters the air flow channel through the flow channel inlet, and then is drawn away by the air blower; wherein the value range of T2 is -10℃≤T2≤71℃.

[0039] Beneficial effects: the temperature adjusting method of the heat insulation cabin device provided by the application not only solves the problem that the dynamometer cannot work normally in a low-temperature environment, but also solves the problem that the flywheel bearing temperature is too high to perform a test in a high-temperature environment test, thereby ensuring the normal work of the power measurement system in the high-temperature and low-temperature environment test of the turboshaft engine. BRIEF DESCRIPTION OF DRAWINGS

[0040] In order to more clearly illustrate the specific embodiments of the present application or the technical solutions in the prior art, the drawings needed to be used in the specific embodiments or the prior art description will be briefly introduced below. Obviously, the drawings in the following description are some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0041] Figure 1 It is a sectional view of a heat insulation cabin device along a third direction for an embodiment of the present application.

[0042] Figure 2 It is a partial sectional view of a heat insulation cabin device for an embodiment of the present application.

[0043] Figure 3 It is a sectional view of a first sub-cabin body and a second sub-cabin body of a heat insulation cabin device for an embodiment of the present application.

[0044] Figure 4 It is a partial enlarged schematic view of A in FIG. Figure 1

[0045] Figure 5 It is a schematic view of the sealing principle of a second sealing member of a heat insulation cabin device for an embodiment of the present application on the upper cabin cover and the lower cabin body.

[0046] Figure 6 It is a partial enlarged schematic view of B in FIG. Figure 1

[0047] It is a schematic view of the structure of FIG. Figure 7 Figure 6

[0048] Explanation of reference signs:

[0049] 10, heat insulation cabin body; 101, heat insulation cabin chamber; 102, calibration interface; 103, air flow channel; 104, flow channel inlet; 105, flow channel outlet; 106, cold air compensation interface; 107, port;

[0050] ​​​11, upper hatch cover; 12, lower cabin body; 1201, first wall body; 1202, second wall body; 121, first sub-cabin body; 122, second sub-cabin body; 13, handle bolt; 14, first sealing element; 15, second sealing element; 151, first layer of sealing; 152, second layer of sealing; 16, reinforcing rib; 17, thermal insulation layer; 18, plastic spraying layer;

[0051] 20, air blower;

[0052] 30, cold air source;

[0053] 40, tee joint;

[0054] 50, sealing assembly; 51, sealing pressing plate; 52, sealing ring; 521, serrated structure;

[0055] 60, sight glass;

[0056] X - first direction; Y - second direction; Z - third direction. DETAILED DESCRIPTION

[0057] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are some but not all of the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0058] In the related art, high and low temperature environment tests are usually completed on a high altitude simulation test bench or a starting rule test bench. A hydraulic dynamometer is used to absorb and measure the output shaft power of an engine during the test. However, the minimum working temperature of the current hydraulic dynamometer is -10°C. In a low temperature environment of -54°C in the high altitude environment cabin, the precision of the tension sensor used by the dynamometer is low, and normal work cannot be guaranteed. In addition, the inlet and outlet water pipelines of the dynamometer are prone to icing in the environment of long time low temperature immersion, and the dynamometer cannot work normally. Since the hydraulic dynamometer and the flywheel rotate at high speed, the bearings use lubricating oil circulation cooling. In a high temperature environment, the bearing temperature is very high due to the heat generated by the friction between the dynamometer and the flywheel and the environmental temperature of the dynamometer itself, which exceeds the use temperature range of the lubricating oil, and the control system of the dynamometer appears protection shutdown, which affects the safety of the engine test run. Therefore, whether in a low temperature environment or in a high temperature environment, the normal work of the dynamometer and the flywheel is tested.

[0059] There are also separately placed dynamometer and flywheel in the high altitude cabin, and the tensile sensor is wrapped separately by using thermal insulation material during low temperature environment test, but the tensile sensor may be frozen due to long low temperature immersion time. The temperature of the flywheel bearing reaches the alarm value after a few minutes during high temperature environment test, and the test cannot continue. There are also start-up rule test benches using heat insulation cabin devices to isolate the dynamometer and flywheel from the high and low temperature environment in the high altitude cabin, but due to the overall processing of the cabin body, disassembly and assembly are difficult, and the flywheel bearing temperature is too high during high temperature environment test, and the test cannot be carried out.

[0060] Therefore, the present application provides a heat insulation cabin device and a temperature adjusting method thereof to overcome the problem that the power measurement system cannot work normally during high and low temperature environment test of the turboshaft engine.

[0061] The embodiments of the present application will be described below in conjunction with Figures 1 to 7 .

[0062] According to the embodiments of the present application, in one aspect, a heat insulation cabin device is provided, comprising:

[0063] The heat insulation cabin body 10, please refer to Figure 1 , comprising an upper cabin cover 11 and a lower cabin body 12, the upper cabin cover 11 and the lower cabin body 12 jointly enclose a heat insulation cabin room 101 for accommodating the power measurement system;

[0064] Please refer to Figure 3 , the lower cabin body 12 has a first wall body 1201 and a second wall body 1202 arranged at intervals, the first wall body 1201 is arranged on the side of the second wall body 1202 facing the heat insulation cabin room 101, and the side of the first wall body 1201 away from the heat insulation cabin room 101 is spaced apart from the second wall body 1202 to form an air flow channel 103;

[0065] Please refer to Figure 2 and Figure 3 , the lower cabin body 12 is provided with a flow channel inlet 104, the flow channel inlet 104 is a flywheel heat dissipation port, one end of the flow channel inlet 104 is communicated with the air flow channel 103, and the other end is communicated with the heat insulation cabin room 101; the lower cabin body 12 is also provided with a flow channel outlet 105, one end of the flow channel outlet 105 is communicated with the air flow channel 103, and the other end is communicated with the air blower 20;

[0066] The lower cabin body 12 is also provided with a cold gas compensation interface 106, one end of the cold gas compensation interface 106 is communicated with the heat insulation cabin room 101, and the other end is communicated with the cold gas source 30.

[0067] It should be noted that the "first direction X" herein refers to the width direction of the heat insulation cabin body 10; the "second direction Y" herein refers to the length direction of the heat insulation cabin body 10; and the "third direction Z" herein refers to the height direction of the heat insulation cabin body 10. The heat insulation cabin device is built in a test room, wherein the test room can be a test environment simulated by a starting rule test bed, and the pressure is usually 47.2 kPa (A) to 101.3 kPa (A); the heat insulation cabin chamber 101 is under standard atmospheric pressure; and the heat insulation cabin body 10 can be fixed on a test platform by bolts.

[0068] In the low-temperature environment test, the outside of the heat insulation cabin body 10 is a low-temperature environment simulated by a starting rule test bed, usually -60℃ to -10℃, the heat insulation cabin chamber 101 is in communication with the atmosphere of the test room, the lower cabin body 12 is provided with an air flow channel 103, a flow channel inlet 104 and a flow channel outlet 105, the flow channel inlet 104 is a flywheel heat dissipation port, the flow channel outlet 105 is connected with a blower 20, the blower 20 works, the atmosphere of the test room enters the heat insulation cabin chamber 101, then enters the flywheel, and then enters the air flow channel 103 through the flow channel inlet 104, transmits heat to the lower cabin body 12, and then is drawn away by the blower 20 through the flow channel outlet 105. In this process, the heat dissipation of the equipment can be drawn away by the blower 20 through the air flow channel 103, and the air is cooled when passing through the air flow channel 103, thereby playing a certain heat preservation role on the heat preservation layer, so as to ensure that the atmosphere in the heat insulation cabin chamber 101 is at room temperature (usually 23℃±5℃), thereby solving the problem that the dynamometer cannot work normally in a low-temperature environment. In the high-temperature environment test, due to the high-temperature environment simulated by the starting rule test bed and the heat dissipation of the dynamometer and the flywheel itself, the temperature in the heat insulation cabin chamber 101 usually reaches 60℃, the cold air compensation interface 106 is arranged on the lower cabin body 12, so that the cold air source 30 is connected with the heat insulation cabin chamber 101 through the cold air compensation interface 106, the cold air and the hot air in the heat insulation cabin chamber 101 are mixed to room temperature (usually 23℃±5℃), then pass through the flow channel inlet 104, the air flow channel 103 and the flow channel outlet 105 in turn, and finally are drawn away by the blower 20, thereby solving the problem that the flywheel bearing temperature is too high to perform the test in the high-temperature environment test, and further ensuring the normal work of the power measurement system in the high-temperature and low-temperature environment test of the turboshaft engine.

[0069] In some embodiments, referring to Figure 1 The upper cabin cover 11 and the lower cabin body 12 are arranged opposite to each other along the third direction Z; the upper cabin cover 11 and the lower cabin body 12 are connected by bolts and / or screws;

[0070] Referring to Figure 3As shown, the lower cabin body 12 comprises a first sub-cabin body 121 and a second sub-cabin body 122, and the first sub-cabin body 121 and the second sub-cabin body 122 are symmetrically arranged along the first direction X; the first sub-cabin body 121 and the second sub-cabin body 122 are connected by bolts and / or screws.

[0071] Further, the first sub-cabin body 121 and the second sub-cabin body 122 are first connected by bolts and / or screws to form the lower cabin body 12, and then the lower cabin body 12 is fixed to the test platform by bolts, and then the upper cabin cover 11 and the lower cabin body 12 are connected by bolts and / or screws.

[0072] Further, when disassembled, the lower cabin body 12 can be separately disassembled or installed with the power measurement system of the heat insulation cabin 101.

[0073] By designing the heat insulation cabin body 10 to be detachably connected with the upper cabin cover 11 and the lower cabin body 12, and designing the lower cabin body 12 to be detachably connected with the first sub-cabin body 121 and the second sub-cabin body 122, it is avoided that the overall machining of the cabin body leads to difficult disassembly, and the equipment disassembly and maintenance time is greatly saved, and the equipment disassembly efficiency is improved.

[0074] In some embodiments, as shown in Figure 1 As shown, the upper cabin cover 11 and the lower cabin body 12 are connected by handle bolts 13, and the disassembly operation is convenient, which is beneficial to the quick installation and disassembly of the upper cabin cover 11 and the lower cabin body 12, and shortens the disassembly time.

[0075] In some embodiments, as shown in Figure 3 As shown, a first sealing element 14 is arranged between the first sub-cabin body 121 and the second sub-cabin body 122, and the first sealing element 14 is used for sealing between the first sub-cabin body 121 and the second sub-cabin body 122;

[0076] As shown in Figure 4 As shown, a second sealing element 15 is arranged between the upper cabin cover 11 and the lower cabin body 12, and the second sealing element 15 is used for sealing between the upper cabin cover 11 and the lower cabin body 12.

[0077] Further, a third sealing element (not shown in the figure) is arranged between the lower cabin body 12 and the test platform, and the third sealing element is used for sealing between the lower cabin body 12 and the test platform.

[0078] By arranging the first sealing element 14 between the first sub-cabin body 121 and the second sub-cabin body 122, and arranging the second sealing element 15 between the upper cabin cover 11 and the lower cabin body 12, it is avoided that leakage occurs when the first sub-cabin body 121 and the second sub-cabin body 122 and the upper cabin cover 11 and the lower cabin body 12 are connected, thereby ensuring the sealing performance of the heat insulation cabin 101.

[0079] Further, the first sealing element 14 can be a silicone rubber strip.

[0080] In some embodiments, referring to Figure 5 As shown, the second seal 15 includes a first layer of seal 151 and a second layer of seal 152, which form a double layer of seal between the upper hatch cover 11 and the lower cabin body 12, thereby effectively avoiding leakage when connecting the upper hatch cover 11 and the lower cabin body 12, and ensuring the sealing of the thermal insulation cabin 101.

[0081] In some embodiments, referring to Figure 3 As shown, the first sub-cabin body 121 and the second sub-cabin body 122 each include a first wall body 1201 and a second wall body 1202 arranged at intervals, and an air flow channel 103 is formed between the first wall body 1201 and the second wall body 1202;

[0082] The first sub-cabin body 121 and the second sub-cabin body 122 are each provided with a flow channel inlet 104 and a flow channel outlet 105;

[0083] Please refer to Figure 1 and Figure 3 As shown, the thermal insulation cabin device further includes a tee joint 40 for connecting the flow channel outlet 105 with the air blower 20.

[0084] By arranging the tee joint 40 to connect the flow channel outlet 105 of the first sub-cabin body 121 and the second sub-cabin body 122 with the air blower 20, the air blower 20 can act on the air flow channels 103 of the first sub-cabin body 121 and the second sub-cabin body 122 at the same time, which is conducive to enhancing the air flow effect in the first sub-cabin body 121 and the second sub-cabin body 122.

[0085] In some embodiments, the power measurement system includes a flywheel connected with the output shaft of the turboshaft engine;

[0086] Please refer to Figure 1 and Figure 4 As shown, the thermal insulation cabin body 10 is provided with a port 107; the thermal insulation cabin device further includes a sealing assembly 50 arranged at the port 107;

[0087] The sealing assembly 50 includes a sealing pressing plate 51 and a sealing ring 52, the sealing pressing plate 51 is connected with the thermal insulation cabin body 10 by bolts and / or screws, and the sealing ring 52 is connected with the sealing pressing plate 51 by bolts and / or screws; the sealing ring 52 is provided with a gill structure 521;

[0088] The output shaft of the turboshaft engine passes through the sealing ring 52 to be connected with the flywheel.

[0089] Further, the sealing ring 52 and the output shaft of the turboshaft engine are in clearance fit.

[0090] Since the internal pressure of the heat insulation cabin 101 is higher than the external environment pressure, in order to prevent the normal temperature air in the heat insulation cabin 101 from leaking into the test room, the sealing plate 51 and the sealing ring 52 are arranged at the port 107 of the heat insulation cabin body 10, so that the output shaft of the turboshaft engine is connected with the flywheel through the sealing ring 52, wherein the sealing ring 52 is provided with the labyrinth structure 521, so as to realize the labyrinth sealing, and further ensure the sealing of the heat insulation cabin 101, and avoid the normal temperature air in the heat insulation cabin 101 from leaking into the test room.

[0091] In some embodiments, referring to Figure 2 , the heat insulation cabin body 10 is further provided with the calibration interface 102.

[0092] The heat insulation cabin device further comprises the sight glass 60 arranged at the calibration interface 102.

[0093] Further, the sight glass 60 is a sight glass with a lamp.

[0094] By arranging the sight glass 60 at the calibration interface 102 of the heat insulation cabin body 10, the running state of the power measurement system in the heat insulation cabin 101 can be observed through the sight glass 60.

[0095] In some embodiments, referring to Figure 1 , Figure 6 and Figure 7 , the heat insulation cabin body 10 is provided with a plurality of reinforcing ribs 16 on the side away from the heat insulation cabin 101.

[0096] The heat insulation layer 17 is filled between the adjacent two reinforcing ribs 16.

[0097] The plastic spraying layer 18 is arranged on the side of the heat insulation layer 17 away from the heat insulation cabin body 10.

[0098] Further, the heat insulation layer 17 can be a polyurethane foam heat insulation material.

[0099] By filling the heat insulation layer 17 between the adjacent two reinforcing ribs 16, the heat insulation effect of the heat insulation cabin body 10 is ensured; by performing the plastic spraying treatment on the side of the heat insulation layer 17 away from the heat insulation cabin body 10 and forming the plastic spraying layer 18, the heat insulation layer 17 is prevented from being sucked into the engine air inlet due to falling off.

[0100] By adopting the heat insulation cabin device provided by the application, the lower cabin body 12 can be separately disassembled, the equipment installation time is reduced from 1.5 days before the improvement to about 0.5 days, and the installation efficiency is increased by about 60%.

[0101] The test results show that, by using the heat insulation cabin device, in a high-temperature atmospheric environment (35 DEG C), when the flywheel speed is 10450r / min, the temperature in the heat insulation cabin 101 is slightly higher than the atmospheric environment, when the flywheel speed is increased to 22000r / min, the temperature in the heat insulation cabin 101 gradually rises to 60 DEG C, at this time, the bearing temperature is above 85 DEG C, low-temperature cold air is introduced into the heat insulation cabin 101, the temperature in the heat insulation cabin 101 gradually decreases to 35 DEG C, the flywheel bearing temperature is kept at about 85 DEG C, the heat insulation cabin 101 reaches temperature balance, and the test requirement in the high-temperature atmospheric environment is met.

[0102] According to the embodiment of the present application, in another aspect, a temperature adjusting method of the heat insulation cabin device is also provided, which comprises:

[0103] When the test is carried out under the first temperature T1 condition, the heat insulation cabin 101 is communicated with the atmospheric environment of the test room, the flow channel inlet 104 is the flywheel heat dissipation port, the flow channel outlet 105 is connected with the air blower 20 through the three-way piece 40, the air blower 20 works, the atmospheric environment of the test room enters the heat insulation cabin 101, then enters the flywheel, and then enters the air flow channel 103 through the flow channel inlet 104, and the heat is transferred to the lower cabin body 12, and then is collected by the three-way piece 40 and is drawn away by the air blower 20, so that the heat insulation cabin 101 is kept in the normal-temperature atmospheric environment; wherein the value range of T1 is -60 DEG C≤T1≤-10 DEG C.

[0104] When the test is carried out under the second temperature T2 condition, the cold air source 30 is connected to the heat insulation cabin 101 through the cold air compensation interface 106, the cold air source 30 is mixed with the hot air in the heat insulation cabin 101 to reach the normal temperature, and then enters the air flow channel 103 through the flow channel inlet 104, and then is drawn away by the air blower 20; wherein the value range of T2 is -10 DEG C≤T2≤71 DEG C.

[0105] It should be noted that the heat insulation cabin is built in the test cabin for test, and T1 and T2 are the temperatures measured in the test cabin.

[0106] The temperature adjusting method of the heat insulation cabin device provided by the present application not only solves the problem that the dynamometer cannot work normally in the low-temperature environment, but also solves the problem that the flywheel bearing temperature is too high to carry out the test in the high-temperature environment, and further ensures the normal work of the power measurement system in the high-temperature and low-temperature environment test of the turboshaft engine.

[0107] Although the embodiments of the present application are described in combination with the drawings, various modifications and variations can be made by those skilled in the art without departing from the spirit and scope of the present application, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A thermally insulated pod arrangement, characterized by The application relates to a heat-insulated cabin body (10) comprising an upper cabin cover (11) and a lower cabin body (12), the upper cabin cover (11) and the lower cabin body (12) jointly enclosing a heat-insulated cabin (101) for accommodating a power measurement system; the lower cabin body (12) is provided with a first wall body (1201) and a second wall body (1202) which are spaced apart, the first wall body (1201) is arranged on the side of the second wall body (1202) facing the heat-insulated cabin (101), and the side of the first wall body (1201) away from the heat-insulated cabin (101) is spaced apart from the second wall body (1202) to form an air flow channel (103); the lower cabin body (12) is provided with a flow channel inlet (104), the flow channel inlet (104) is a flywheel heat dissipation opening, one end of the flow channel inlet (104) is communicated with the air flow channel (103), and the other end is communicated with the heat-insulated cabin (101); the lower cabin body (12) is further provided with a flow channel outlet (105), one end of the flow channel outlet (105) is communicated with the air flow channel (103), and the other end is communicated with a blower (20); the lower cabin body (12) is further provided with a cold air compensation interface (106), one end of the cold air compensation interface (106) is communicated with the heat-insulated cabin (101), and the other end is communicated with a cold air source (30). The upper cabin cover (11) and the lower cabin body (12) are oppositely arranged along a third direction (Z); the upper cabin cover (11) and the lower cabin body (12) are connected through bolts and / or screws; The lower cabin body (12) comprises a first sub-cabin body (121) and a second sub-cabin body (122), the first sub-cabin body (121) and the second sub-cabin body (122) are symmetrically arranged along a first direction (X); the first sub-cabin body (121) and the second sub-cabin body (122) are connected through bolts and / or screws. The upper cabin cover (11) and the lower cabin body (12) are connected through a handle bolt (13). A first sealing member (14) is arranged between the first sub-cabin body (121) and the second sub-cabin body (122), and the first sealing member (14) is used for sealing the first sub-cabin body (121) and the second sub-cabin body (122); 2. The thermally insulated pod apparatus of claim 1, wherein, A second sealing member (15) is arranged between the upper cabin cover (11) and the lower cabin body (12), and the second sealing member (15) is used for sealing the upper cabin cover (11) and the lower cabin body (12). The second sealing member (15) comprises a first layer of sealing (151) and a second layer of sealing (152), and the first layer of sealing (151) and the second layer of sealing (152) form a double-layer sealing between the upper cabin cover (11) and the lower cabin body (12).

3. The thermally insulated pod apparatus of claim 2, wherein, ​ 4. The thermally insulated pod apparatus of claim 2, wherein, ​ ​ 5. The thermally insulated pod apparatus of claim 4, wherein, ​ 6. The thermally insulated pod apparatus of claim 2, wherein, The first sub-cabin body (121) and the second sub-cabin body (122) each comprise the first wall body (1201) and the second wall body (1202) arranged at intervals, and the air flow channel (103) is formed between the first wall body (1201) and the second wall body (1202) at intervals; The first sub-cabin body (121) and the second sub-cabin body (122) each are provided with the flow channel inlet (104) and the flow channel outlet (105); The heat insulation cabin device further comprises a tee joint (40) for connecting the flow channel outlet (105) with the air blower (20).

7. The thermally insulated pod apparatus of claim 1, wherein, The power measurement system comprises a flywheel connected with an output shaft of the turboshaft engine; The heat insulation cabin body (10) is provided with a port (107), and the heat insulation cabin device further comprises a sealing assembly (50) arranged at the port (107); The sealing assembly (50) comprises a sealing pressing plate (51) and a sealing ring (52), the sealing pressing plate (51) is connected with the heat insulation cabin body (10) by bolts and / or screws, and the sealing ring (52) is connected with the sealing pressing plate (51) by bolts and / or screws; the sealing ring (52) is provided with a grid structure (521); The output shaft of the turboshaft engine is connected with the flywheel through the sealing ring (52).

8. The thermally insulated pod apparatus of claim 1, wherein, The heat insulation cabin body (10) is further provided with a calibration interface (102); The heat insulation cabin device further comprises a sight glass (60) arranged at the calibration interface (102).

9. The thermally insulated pod arrangement according to any of claims 1-8, characterized in that The heat insulation cabin body (10) is provided with a plurality of reinforcing ribs (16) on a side away from the heat insulation cabin chamber (101); A thermal insulation layer (17) is filled between adjacent two reinforcing ribs (16); A plastic spraying layer (18) is arranged on a side of the thermal insulation layer (17) away from the heat insulation cabin body (10).

10. A method of temperature adjustment of a thermally insulated chamber device according to any one of the preceding claims 1 to 9, characterized in that, Comprise: When tested under a first temperature T1, the heat insulation cabin chamber (101) is in communication with an atmosphere of a test room, the flow channel inlet (104) is a heat dissipation port of the flywheel, the flow channel outlet (105) is connected with the air blower (20) through the tee joint (40), the air blower (20) is working, the atmosphere of the test room enters the heat insulation cabin chamber (101), then enters the flywheel, and then enters the air flow channel (103) through the flow channel inlet (104), so that heat is transmitted to the lower cabin body (12), and then the heat is collected by the tee joint (40) and is drawn away by the air blower (20), so that the atmosphere in the heat insulation cabin chamber (101) is normal temperature; wherein the value range of T1 is -60℃≤T1≤-10℃; When tested under a second temperature T2, a cold gas source (30) is connected to the heat insulation cabin chamber (101) through the cold gas compensation interface (106), and the cold gas source (30) is mixed with hot gas in the heat insulation cabin chamber (101) to reach normal temperature, and then enters the air flow channel (103) through the flow channel inlet (104), and then is drawn away by the air blower (20); wherein the value range of T2 is -10℃≤T2≤71℃.

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